Manufacture of blade channels of turbomachine rotors

Patent metadata

Field	Value
Publication number	US-2016333697-A1
Application number	US-201615150721-A
Country	US
Kind code	A1
Filing date	May 10, 2016
Priority date	May 12, 2015
Publication date	Nov 17, 2016
Grant date	—

Abstract

A method for manufacturing blade channels of turbomachine rotors, in particular gas turbine rotors, with integrated blades. The method comprises producing a multiplicity of arrangements, offset with respect to one another in a circumferential direction, of bores proceeding from a radially outer shell surface of the rotor, at least two bores of at least one arrangement being offset with respect to one another in an axial and/or circumferential direction such that said bores engage into one another and form a slot; and producing pressure and suction sides of blades by material removal in the slots.

First claim

What is claimed is:

1 . A method for manufacturing blade channels of a turbomachine rotor with integrated blades, wherein the method comprises:
producing a multiplicity of arrangements, which are offset with respect to one another in a circumferential direction, of bores proceeding from a radially outer shell surface of the rotor, at least two bores of at least one arrangement being offset with respect to one another in an axial and/or circumferential direction such that said bores engage into one another and form a slot; and producing pressure and suction sides of blades by material removal in the slots.

2 . The method of claim 1 , wherein a radial height of at least one of the produced bores amounts to at least 75% of a blade height of an adjacent pressure and/or suction side of the blades.

3 . The method of claim 1 , wherein a radial height of at least one of the produced bores amounts to at least 90% of a blade height of an adjacent pressure and/or suction side of the blades.

4 . The method of claim 1 , wherein a spacing of at least one of the bores in the circumferential direction from an adjacent pressure side and from an adjacent suction side differs by at most 10%.

5 . The method of claim 1 , wherein a diameter of at least one of the bores is at least 30% and/or at most 90% of a minimum spacing in a circumferential direction between an adjacent pressure side and suction side.

6 . The method of claim 1 , wherein a diameter of at least one of the bores is at least 50% and/or at most 85% of a minimum spacing in a circumferential direction between an adjacent pressure side and suction side.

7 . The method of claim 1 , wherein at least two bores of at least one of the arrangements have the same diameter.

8 . The method of claim 1 , wherein at least two bores of at least one of the arrangements have different diameters.

9 . The method of claim 1 , wherein cross sections of at least two adjacent bores of at least one of the arrangements overlap one another by at least 10% and/or at most 90%.

10 . The method of claim 1 , wherein a drilling axis of a drilling tool during the production of at least one of the bores is inclined by at most 35° with respect to a radial direction of the rotor.

11 . The method of claim 1 , wherein a drilling axis of a drilling tool during the production of at least one of the bores is inclined by at most 15° with respect to a radial direction of the rotor.

12 . The method of claim 1 , wherein at least one of the bores is produced in a single working step.

13 . The method of claim 1 , wherein a bore that is produced first in at least one of the arrangements is produced so as to be spaced apart in an axial direction from mutually oppositely situated face sides of the rotor.

14 . The method of claim 1 , wherein at least one of the slots formed by the bores that engage into one another is open in the axial direction toward one or both of the mutually oppositely situated face sides of the rotor.

15 . The method of claim 1 , wherein, firstly, at least two slots that are adjacent in the circumferential direction are formed by way of the bores that engage into one another, and subsequently, the pressure side and suction side of a blade are produced by material removal in said slots.

16 . The method of claim 1 , wherein the pressure side and/or suction side of at least one of the blades is produced by repeated material removal, and/or material removal blockwise in a radial direction, in the slots.

17 . The method of claim 1 , wherein the pressure side and/or suction side of at least one of the blades is produced by cutting and/or contactless material removal in the slots.

18 . The method of claim 1 , wherein the pressure side and suction side of at least one of the blades are produced by material removal in encircling fashion.

19 . A turbomachine rotor with integrated blades, wherein said turbomachine rotor is manufactured by the method of claim 1 .

20 . A machine tool for manufacturing the turbomachine rotor of claim 15 , wherein the tool comprises a drilling tool for producing the multiplicity of arrangements, which are offset with respect to one another in a circumferential direction, of bores, and a tool for producing the pressure and suction sides of the blades by material removal in the slots formed by the bores.

Assignees

• MTU Aero Engines AG

Inventors

• Steinert Wolfgang
• Seidl Adolf

Classifications

• B23P13/02

  in which only the machining operations are important · CPC title

• B23C2215/44

  Turbine blades · CPC title

• F05D2230/10

  by removing material · CPC title

• B23H9/10

  Working turbine blades or nozzles · CPC title

• B23C2220/56

  Plunge milling · CPC title